Projectile construction



June 2l, 1960 G. E. BARNHART 2,941,469

PROJECTILE CONSTRUCTION Filed Nov. l5, 1955 za /7 I ,3 Ff A. y i ,4 i 6 ,o

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FUnited States Patent O PROJECTILE :CONSTRUCTIDN George E. Barnhart, 2228 New York Drive, Altadena, Calif.

Filed Nov. 15, 1955, Ser. No. 546,992

4 Claims. (Cl. 102-49) This invention relates generally to projectiles and relates more specifically to a firearm or rocket propelled type of projectile that may be used for sport or military PU1`P0SS- v Contemporary weapon and projectile designs have tended toward the provision of larger, higher Velocity projectiles in order to provide the accuracy, impact forces and penetration required for destructive purposes. However, with increased size and complication in projectiles, manufacturing costs become inherently higher, and storage and transportation facilities become seriously taxed, especially for those types of firearms commonly carried by an individual who must also carry sufficient ammunition for the firearm.

v l Additionally, in use of projectiles of various types, considerably greater accuracy may be obtained through rotation of the projectile during iiight. This rotating characteristic is generally accomplished by means of riti-ing in the barrels of launching weapons, by fins or directional appendages from the projectile or by propulsive reaction forces induced by an explosive substance carried by the projectile. Each of these factors alone or in combination, either add to the effective weight of the projectile, reduce its eectiveness and proper ight characteristics due to extensions of portions thereof into the slipstream, create a centerof gravity changing problem, or create excessively heavy structures, thus to obviate the use thereof with relatively small hand-carried portablerdevices such as rifles, pistols or small rocket launchers. v Additionally, with ,projectiles over a predetermined length, considerable dilliculty is experienced relative to tumbling and erratic flight characteristics.

Accordingly, Vit has beenfound to be necessary to employ means associated with a projectile for inducing rotation thereto during ight in order that the range, accuracy, penetrating power and effectiveness may be increased.'` In order to maintain these factors, itis important that means employed for inducing better flight conditions, `better explosive effectiveness and rotation of the projectile,- be inherent in a construction that is similar njsize to heretofore vknown projectiles. In other words, it isfnecessarythat this means be arranged in combinationand cooperation with known portions of the projectile -in such a manner as to enable provision thereof in space envelopes substantially equal to that provided in contemporary structures. t A

In accordance with the beforementioned desirable characteristics of p'rojectiles, it is one important object of the invention to provide a projectile having novel flight characteristic improving means.

It is another important object of the invention to provide a projectile having novel 'in-flight rotation inducing means associated therewith.

. Itis a further important object of the invention to pro-` vide novel'means for accepting and expelling Vair through.

n '2,941,469 Patented June 21, 1960 jectile having novel rotation inducing means arranged in combination with an impact responsive explosive charge and means for detonating said charge.

Another object hereof is to provide a novel projectile having means for effecting deep penetration into a target through usually known armor plating.

It is a still further object of the invention to provide an -in-iiight rotating projectile having combination projectile including Ia modified head portion, a propulsive charge and jet reaction nozzles;

Fig. 4 is a further modied form of the present projectile including a further modified head structure, both a propulsive charge and an explosive charge, and novel ignition means for the explosive charge;

Fig. 5 is a still further modified form of the projectile including an explosive charge and an independent leading end portion; and

Fig. 6 is a fragmentary view showing another moditied form of projectile head construction.

With reference to the drawing, and with reference primarily to Fig. l, the projectile is indicated generally at 10 and is adapted for use in connection with a case 11 having a reduced diameter neck portion 12 and a flanged rearward end portion 13. The rearward portion 13 is adapted for reception of a suitable cap 14, there being la quantity of explosive powder 15 arranged within the case and retained therein by means of wadding 16.

As shown primarily in Figs. l and 2, the neck 12 of the case 11 is generally longitudinally and helically indented as at 17 with the indentations therein being cooperable with longitudinal elongated generally helical grooves 18 in the outer surface of the projectile 10. Thus, as the projectile is propelled in initial movement thereof, the action of the indentations 17, cooperating with the grooves 18, provides for initial rotation of the projectile as it leaves the end of the case 11.

With reference primarily to Fig. 2, the projectile -10 further includes an elongated body portion 20 that is primarily solid, there being a recess 21 formed in the leading end"portion of the body. The recess 21 has a bottom vend wall 22 defined by a partition which, in the form of the invention shown in Fig. 2, extends from this bottom wall to the trailing end portion 23 of the projectile. Side -vvalls 24 of the recess are defined by walls of the body 20 and are preferably airfoil shaped to deline a throat `within the contines of the recess. The leading edge ofLthe projectile surrounding the recess 21 is relatively sharp, as at 25. The bottom wall 22 of the recess 21 is J.formed with an axially arranged, generally conical portion 26 that is annularly contoured as at 27 to provide a srnooth connection with the side walls 24 of the recess. v

In order to provide ffor rotation of the projectile during in-flight conditions, a plurality of generally equally spaced, helically disposed, generally rearwardly and radially directed passageways 28 are provided through the wall of the@ body 20 and communicate between an end of the refess 21 adjacent the bottom wall 22 thereof and the elxterior surface of the body 20. Thus, during in-ilight conditions, air will be rammed into the recess 21, will be directed outwardly from the base portion thereof by means of the conical portion 26 and discharged from the recess through the passageways 28 in a generally helical manner whereby to induce rotation of the projectile. Furthermore, forward turbulence of air surrounding the projectile is considerably reduced by passage thereof through the recess 21 and the passageways 28, thereby providing smooth flight characteristics, rotation of the projectile to establish stability thereof and longer uninterrupted flight conditions.

With reference to Fig. 3, this modified form of the present projectile is indicated generally at 30 and has a body portion 31, with a recess 32 formed in the for ward or leading end thereof. Outer walls 33 of the recess are cylindrical and thin-walled in this form of the invention, with the leading end thereof sharpened as at 34. A conical portion 35 is positioned in the base of the recess and on one side of a partition 36, there being a plurality of helically disposed passageways 37 between the bottom of the recess 32 and the exterior surface of the projectile. Additionally, in this form of the invention, a chamber 38 is formed in the rearward portion thereof, this chamber being adapted for retention of a propulsive charge 40. A'rear wall 41 of the chamber 38 has a plurality of helically disposed exhaust nozzles 42 therethrough with an igniter 43 being positioned generally in the central area of the end wall 41. The body portion 31, the partition 36 and end wall 41 are formed as an integral unit as by any well-known means of manufacturing.

With further reference to the form of the invention shown in Fig. 3, it is to be noted that the leading edge of the thin-walled portion 33 is provided with a plurality of generally external grooves 44 that are generally helically disposed rearwardly and slightly radially extending, with the depth of these grooves being reduced as they are formed rearwardly. While the present structure is shown as being associated with the thin-wall section 33, it may easily be seen and understood that the grooves `44 may be employed about solid leading end portions of the projectile and may be of any number. In this form of the invention, it has been found to be advantageous that the leading edges of the section 33 and intermediate the leading end of the grooves 44 be relatively sharp and contoured as at 45 between ends of the grooves. Thus, either separately or in combination with the helical passageways 37, the grooves 44 serve to stabilize and direct the leading end of the projectile by inducing rotation thereof, due to the eEect of ram air passing therethrough and the circumferential vcomponent imparted thereby. Thus, even though th projectile of this invention may be relatively long', an accurate stability is maintained during flight thereof due to the configuration of the leading end.

This fact has been clearly established in How tests utilizing conditions 4approximately those encountered in high speed flight of the projectile. In t'nese tests identical structures were utilized, similar to the various forms of this invention, with flow threover being directed with the control grooves at the leading end and thereafter at the trailing end. Results of these tests indicated that considerable advantage and gain in rotating characteristics are available. t

In reference to the form of the invention shown in Fig. 4, the projectile disclosed therein is indicated generally at 50 and includes a body portion 51. The body portion 51 is provided integrallyV with a leading end reduced diameter contoured port/tion ,52, having an axial bore 53 defining a recess A partition 54 defines one end of a chamber 95, there being an annular space 56 defined between the ition 54 and the leading end portion 52. A plurality of struts 57 or the like, support the leading end portipn-SZ, relative to the par- 4 tition 54. The outer surface of the partition 54 is provided with a plurality of rearwardly and radially extended, generally helically disposed vanes 58. During flight conditions, ram air passes inwardly through the bore 53 and outwardly through the annular space 56 and over the vanes 58, whereby to induce rotation of the projectile body. The projectile body 51 is provided with a reduced diameter necked-in area 6i) that defines a configuration similar to a bow wave structure. This particular arrangement reduces turbulent effects of air passing over the surface of the projectile, thus to create improved flight characteristics thereof.

With reference to Fig. 4, the chamber 55 is divided into a pair of sections by means of a wadding type partition `61, there being a propulsive charge `62 positioned in the rearwardmost portion of the chamber 55 and an explosive charge 63 positioned in the forwardmost portion of the chamber 55. The rearward end of the body portion 51 is provided with a closure member 65 that is retained therein as by any suitable means, there being propulsion nozzles provided through the closure 65 and the igniter 66 that is arranged in a manner to ignite the charge 62 as the projectile is launched. Furthermore, the partition 54 is provided with an axial bore 67 in which a rod 68 is slidably positioned. The forward end of the rod 68 extends to a point within the bore 53. The rearward end of the rod 68 extends through the explosive charge 63 for operable cooperation with an igniter 70 positioned adjacent the partition 61 in the rearward area of the charge 63. Thus, when the projectile 50 stri-kes a target, slight mushroomting will be accomplished -in the forward end thereof, thus to cause movement of the Arod 68 inwardly and energization of the igniter 70. The igniter 70, together with the previously described igniters 43 and 66 may be of any welldknown, suitable types and may employ Fomanite or the like type of explosive substance.

The projectile of Fig. 4 is therefore provided with stabilizing action and additional propulsive force for flight to a target and means by which further destruction of the target may be accomplished when contact is made therewith.

In the form of the invention shown in Fig. 5, it is to be noted that this form, indicated generally at 80, includes a body portion 81 and a forwardly directed leading end recess 82. The leading end of the body portion 8l is contoured inwardly as at 83 to provide a partition between the recess 82 and the chamber 84 formed within the body portion 81. In this form of the invention, the recess 82 is defined by an elongated annular thin-walled cylindrical extension member 85 that is permanently secured to the body portion 81 as by formation of a portion 86 thereof in an annular groove 87 in the body portion 81. The leading end of the cylindrical member 85 is provided with a plurality of sharpened cutting edge serrations 88 thereabout, these serrations being sharpened in both axial and circumferential directions for a purpose to be hereinafter more fully described. The member 85 is further provided with a plurality of rearwardly and radially outwardly extending, generally helically disposed grooves or depressions 90, the rearward ends of whichv communicate with openings 91 through the cylindrical member 85. In addition to the beforementioned features of the form of the projectile shown in Fig. 5, the leading end portion or partition 83 is provided with an igniter 92 for an explosive charge 93 positioned within the chamber 84. The rearward end of the body 81 is closed by means of an integral partition 94.

In the form of the invention shown in Fig. 5, employing the principles taught in this invention, it may be seen that in-flight rotating components will be induced by delivery of ram air into the recess 82 and outwardly therefrom i through the grooves and rearward openings 91 thereof. Additionally, the sharpened serrations 88, upon contact with a target, serve no`t only to cut through outer surface of the target but also tend to pivot the projectile in a direction whereby to ,dispose the projectile more normal to the target. In other words, the center of gravity of the projectile is such as to create a moment about the leading and bitting end, actually to direct the axis of the projectile directly toward the target. This construction is particularly advantageous when the projectile strikes a target Vat anglesother than 90o thereto, to eect penetration thereof rather than mere ricochet therefrom. Slight mushrooming of the forward end of the projectile will thereafter be accomplished by destruction of the cylindricalmember 85, whereupon the igniter 92 will be contacted, thus to explode a charge 93 and devastate the tai-get. i .l n

In Fig. 6 is shown a modified projectile head construction wherein a leading end thereof is sharp pointed as at 100, there being rearwardly-and radially extending, generally helically disposed passageways 101 surrounding the leading end 100. The outer portions of the passageways 101are shrouded as by a shroud portion 102, there being a partition 103 separating the leading end 100 from a chamber 104, which may contain either a propulsion or explosive charge 105. The leading end 100, together with the shroud portions 102, may be shaped similar to a drill in order that more effective penetration of the projectile may be accomplished while still maintaining other flight features taught herein for inducing in-ight rotation of the projectile.

In all the various forms of the invention, as the projectile strikes a target, the forward end portion thereof will be mushroomed as shown by the dotted lines in Fig. 2, thus to create extensive damage and/ or destruction of the target. Thus, the effects normally experienced in connection with hollow nose projectiles will be inherent in the present projectile. Additionally, the present projectile provides for rotation thereof during in-ight conditions thus creating a more stabilized situation. With the forms of the invention shown in Figs. 3 and 4, as the projectile leaves the case 11, continued acceleration will be experienced for a short period due to the effect of the propulsive charges `40 and 62 respectively, and the reaction thereof through helically disposed discharge nozzles 42 and 65. Discharge through the nozzles 4Z and 65 also serves to create a rotating condition for the projectile, thus adding to the stability thereof during in-ight conditions. Naturally, each of the forms of the invention shown in Figs. 3, 4 and 5 may have the longitudinal grooving provided on the exterior surface thereof as shown in Figs. 1 and 2 in order to induce initial rotation to the projectile without the use of riing or other configurations within the barrels.

Thus it may be seen that the projectile of this invention and several modified arrangements thereof may advantageously be used in various situations including military activity with considerably improved ight characteristics and destructive force being inherent in the operation and use thereof. Additionally, the projectile is of such construction as to enable provision of the device thereof in relatively small projectiles as for example, between 22 and 50 calibre devices and may be launched by means of any usual firearm or launching device, without the use of special launching equipment or ring mechanisms.

Having thus described the invention and the several embodiments thereof, it is desired to emphasize the fact that many further modifications may be resorted to in a manner limited only by a just interpretation of the following claims.

I claim:

l. A projectile comprising, in combination: an elongated generally cylindrical body having leading and trailing ends; a transverse closure for said trailing end of said body; a transverse partition in said body, said partition being spaced from said leading end, one side thereof defining a bottom of a recess in said leading end of said body, said one side of said partition having a generally cone shaped contour extending outwardly from an axial, forwardly directed apex thereon; a reduced diameter throat formed from side walls of said recess; an annular sharp leading edge about said recess; a plurality of helically disposed, generally rearwardly and radially directed passageways disposed through said body and communicating between an inner end of said recess from a junction of said sides of said recess and said partition to an outer surface of said body; a propulsive charge carried in said body rearwardly from said recess; means to ignite said propulsive charge; reaction discharge nozzle means through said transverse closure; an explosive charge carried in said body rearwardly from said recess; means disposed in a rearward portion of said explosive charge to ignite said explosive charge; and means operable by impact of said leading end of said projective for triggering said igniting means.

2. A projectile for use with a shell casing comprising, in combination: an elongated generally cylindrical integral body having contoured leading and trailing end portions; an integral transversely disposed closure portion for said trailing portion of said body; a transversely disposed partition in said body, said partition being spaced from said leading end, one side thereof defining a bottom of a recess in said leading end portion of said body, said one side of said partition having a generally cone shaped contour extending outwardly from an axial, forwardly directed apex thereon; an 'annular reduced diameter airfoil shaped throat formed from side walls of said recess; an annular sharp leading edge about said recess; a plurality of equally spaced helically disposed generally rearwardly and radially directed passageways disposed through said body and communicating between an inner end of said recess from a junction of said sides of said recess and said partition to an outer surface of said body for induc-V ing rotation of said projectile While in ight; a pair of chambers in a rearward portion of said body, the forwardmost of said chambers containing an explosive charge, the rearwardmost of said chambers containing a propulsive charge; ignition means for said charges; and helical nozzle means disposed through said closure portion for permitting expulsion of exhaust products from said propulsive charge.

3. A projectile for use with a shell casing comprising, in combination: an elongated generally cylindrical integral body having contoured leading and trailing end portions; an integral transversely disposed closure portion for said trailing portion of said body; a transversely disposed partition in said body, said partition being spaced from said leading end, one side thereof defining a bottom of a recess in said leading end portion of said body, said one side of said partition having a generally cone shaped contour extending outwardly from an axial, forwardly directed apex thereon; an annular reduced diameter airfoil shaped throat formed from side walls of said recess; an annular sharp leading edge about said recess; a plurality of equally spaced helically disposed generally rearwardly and radially directed passageways Adisposed through said body and communicating between an inner end of said recess from a junction of said sides of said recess and said partition to an outer surface of said body for inducing rotation to said projectile while in Hight; a pair of chambers in a rearward portion of said body, the forwardmost of said chambers containing an explosive charge, the rearwardmost of said chambers containing a propulsive charge; an impact operable igniter for said explosive charge, said igniter being positioned at saidl apex on said partition and'extending into said recess; ignition means for said propulsive charge; and helical nozzle means disposed through said closure portion for permitting expulsion of exhaust products from said propulsive charge.

4. In a vehicle adapted for travel in a Huid medium,

I the combination of: an elongated generally' cylindrical body having leading and trailing ends; a transverse closure for said trailing end of said body; a transverse partition in said body, said partition being spaced `from said leading end, one side thereof defining a bottom of a recess in said leading end of said body, said one side of said partition having a generally cone shaped contour extending outwardly from an axial, forwardly directed apex thereon; a reduced diameter throat formed lfrom side walls of said recess; an annular sharp leading edge about said recess; a plurality of helically disposed, generally rearwardly and radially directed passageways disposed through said body and communicating between an inner end of said recess from a junction of said sides of said recess and said partition to an outer surface of said body; a bow .wave structure formed in an exterior surface of said body immediately rearwardly from a discharge end of said openings; 'a propulsive charge carried in said body rearwardly'from said recess; means to ignite said propulsive charge; reaction discharge nozzle means through said transverse closure; an explosive charge carried in said body rearwardly from said recess; means V8 disposed kin a rearward portion of said explosive ycharge to ignite said explosive charge; and means operable by impact of said leading end of said projectile'for triggering said igniting means. l

References Cited in the le of this patent UNITED STATES PATENTS Matteson Nov. 19, 1861 35,103 Mansfield Apr. 29, 1862 644,361 Luciani Feb. 27, 19(1) 922,638 Spencer May 25, 1909 1,012,455 Scott Dec. 19, 1911 1,176,082 Moore Mar. 21, 1916 1,327,531 Durham Jan. 6, l1920. 1,333,199 Barthelemy Mar. 9, 1920 1,376,530 Greener May 3,'1921 1,384,841 Lundell July 19, 1921 1,758,635 Wieser May 13, 1930 2,206,809 Denoix July 2, 1940 2,624,281 McNally Ian. 6, 1953 

